Turbine driven pump



' Mwls Oct. 27, 1959 P. T. ANGELL. Erm.

TURBINE DRIVEN PUMP Filed May 4, 1954 5 Sheets-Sheet 1 B'erce T' A1256!!w F0/be U/jborn 7 2f H5 Oct. 27, 1959 Filed May 4. 1954 P. T. ANGELL.ErAL 2,910,005

TURBINE DRWIVEN PUMP 5 Sheets-Sheet 2 Inra-Tlfn T5 oa. 27, 1959 p. T.ANGELL Em. 2,910,005

v TURBINE DRIVEN PUMP Filed may 4, 1954 s sheets-sheet s Pierce T Ange/24 .7? [zeri Cjborfz E: Li l #MH Z L ?E- TURBINE DRIVEN PUMP Pierce T.Angell, Pepper Pike Village, and Robert Cliborn, South Euclid, Ohio,assignors to Thompson Ramo Wooldridge. Inc., a corporation of OhioApplication May `4, 1954, serial No. 427,599

-s claims. (c1. s- 87) Ftentedoct27, 1959 Tice Z rotor in combinationwith a key extending radially and nonrotatively secured to the shaftcarrying said rotor.

.Another feature of the present invention is the provision, ofconcentric turbine inlet and pump outlet fluid carrying chambersconcentrically mounted about bearing means for ar combined turbine and,pump whereinthe extremely strong with ta minimum of weight and a maximumoffluid'ow per inch of diameter of the turbine rotor. These requirementsare extremely important in the eicient design of modern light weightequipment and have. been considered absolutely necessary in order toutilize the compressed gases available for a power source on modern jetaircraft, for example.

By the present. invention, a simplified and substantially improvedturbine rotor structure has been provided while retaining an extremelysmall turbine rotor diameter and while maintaining the cost ofmanufacture' at a minimum.

InV reducingthe cost of theV present turbine apparatus, .applicants havesimultaneously achieved substantially greatervstrength therebypermitting high operating speeds with a minimum of operationalbreakdowns. Further, through the use of a novel, compact, nestingarrangement wherebyl the small diameter turbine inlet is positioned inimmediate. contact with the high pressure outlet of the associated uidpump, cooling of the bearings of the combined turbine andl pump iseffectively provided. Further, cooling of the compressed fluid isprovided in situations where the temperature of the compressed fluidreachesy an undesirably high level. Thus, `through the compact designherein disclosed, a highly ecient, yet extremely simpleV turbine andpump structure is provided i rshown in Figure l;

wherein great durability is provided in the rotating structuralcomponents and, further, unusually ei`cient cooling is achieved.

It is therefore an object of the present invention to provide a novelcombined turbine and pump structure.

Another object of the, present invention is to provide a novel turbinerotor having a novel drive connection to the, turbine output shaft.

Still a further object of the present invention is to provide` asimplified turbinenozzle and rotor construction.

Yet another object of the present invention is to providey a novelinterrelated turbine inlet lluid and outlet iluid heat exchangercooperating with the bearings supporting both the turbine and the pumpdrive shafts.

Still another object of the present invention is to provide a novelspring retained drive connection for turbine rotors and the like. w

Yet another object is to provide a method of manufacturing turbinenozzle passages in a simplified manner.

A feature of the present invention is the provision of a radiallyextending key way in the end face of the turbine bearing meanssupportsthe drive shaft for both said turbine and said pump and ispositioned in immediate heat transmitting relationship to both theturbine inlet iluid and the pump outlet uid.

Still a further feature of the present invention is the provision of asimplified two piece pump vand turbine housing in which the pump outletuid passes in direct contact with the outside of the turbine housing :toeffect heat transfer therewith. I

Another object of the present invention is to provide a lturbine havinga large ratio of ow area per inch of turbine rotor diameter. 'i

A further object of the, present invention is to provide a novel driveconnection between the turbine rotor'and l its supporting shaft wherebyradial expansion and, hence, axial contraction of the rotor4 isautomatically compensated for and looseness at high rotational speedsthereby eliminated.

Still Vother and further objects and features of the present inventionwill at once become apparent to those skilled in the art fromthe'consideration of the attached ,sheets of drawings wherein: s Figurel is an elevational view in cross section of Athe combined turbine andpump of the present invention;

Figure Z- is an end` elevational view of the structure Figure 3` isacross-sectional view taken along the line III--III of Figure l; j

Figure 4 is a kpartial elevational view in cross-section showing amodified form of turbine nozzle and' taken along the line similar toIV'.IV of Figure 2;

Figure 5 is a partialend elevational view of the modified` form ofnozzle shown in Figure 4;

Figure 6 is a developed view of the blading of the turbine nozzleconstructed according tothe embodiment shown in Figures l and 2;

Figure 7 is a developed view of the blading'of the turbine. nozzles ofthe present invention and constructed in accordance with the embodimentthereof shown in Figures 4- and. 5; and' Figure 8 -is' a cross-sectionalview of the turbine rotor drive transmitting key and locking devicetaken along thelines VIII- VIII of Figure l.

As shown on the drawings: Y The Combined turbine drive and uid pumpofthe pres-'- ent invention is shown in somewhat greater than full sizedimensions in Figure l. There, the right hand portion of the apparatusoperates as a turbine While the letthaud end of the devicetransforms thework energy supplied by the turbine into a centrifugal pumping actionfor pressurizing a liquid or gaseous medium such as, for example,gasoline or similar fuel for aircraft. 'y As shown in the figures theassembly comprises a three part housing 10 composed of a central pumphousing 11, a pump inlet housing 12 and an air circulating housing 13Vprovided with an axial air ow controlling 'housing 14; The centralkhousing 11 is provided with an axially extending bore 15 in which adrive shaft 16 is mounted by means of conventional ball bearings 17 and18. Axial movement of the shaft 16 is prevented by the shoulders 19 inthebore 15, the metal spacing sleeve 20, the spring retainer 21 andtheabutment wall 22 secured to the housing 11- by means countersunk screws23. y. The drive shaft 16 carries a turbine rotor Z5-at its right hand,or turbine, end. The rotor 25l is abutted against the thrust abutment 26and is maintained axially positioned thereagainst by means of the radialkey 27 positioned in a diametrical slot 28 in the shaft 16 andmaintained in position by means of the threaded nut 29.

As maybe seen from a consideration of Figures l and 2 ,'air enteringthehousing l13 by means'of'the air inlet '1311 passes around thecircumference of the air circulation .housing 13 Yand is directedaxially' `therefrom through the' nozzle plate 30 by the nozzle vanes 30aas indicated bythe arrows 31.V As may be seen from, Figure 1,` theVnozzle .plate 30, which wi1l. be more fully discussed "below issecuredby screws 32 tothe intermediate support 'member 33 which is inpturnsecured to the central housing 1 1 by means ofthe screws 23. The in#termediate support 33 may be integral with or otherwise permanentlysecured to the innermost portion 13b of the housing'13.or, as analternative method of manufacture, the support 33 may instead bear asliding t relationship with the portion 13b at 33a to thereby provide aHuid tight seal. 'Y

In the general arrangement above set out, compressed air introduced inthe direction of the arrow shown in Figure 4V2 through the inlet 13awill pass through the nozzle passages 30b and impinge upon the vanes 25aof the turbine rotor 25 thereby rotating the shaft 16 through the key,27.l The shaft 16 is drivingly connected to the centrifugal pump rotor35.

y The pump rotor 35 draws low pressure fuel or the like from the inlet36 and delivers the fuel through centrifugal action `to, the rotoroutlet37. `From thence it travels axiallythrough the diluser passages 38 to'the collecting ring 39 from whichgthe-fuel is delivered through theThe'r'o'tor 35 is maintained in axial and radial alignment by means ofthe bearing and wear'surfaces 41 and 42 as well as by the bearings 17and 18. Although the rotor 35 may be secured to the shaft 16 'in anumber of pressed gas in the chamber 13. However, it is desired that thetemperatures in both chambers or housings 11 and 13 be maintained at aminimum and that the temperature of the bearings 17 and 18 likewise beretained at a minimum value. Therefore, the arrangement shown in thepresent invention provides a maximum possible attainment of this end byplacing the chambers 11 and 13 in heat transfer relationship with eachother and with the bearings 17 and 18 whereby the temperature of allthree will be maintained at a minimum, average value determined by thecoolest of the three elements.

As has been above generally described, the rotor of the turbineisdrivingly connected to the shaft 16 by means of a key 27. The key 27 isexceptionally effective in connecting the rotor to the shaft 16 forseveral reasons. In the first place, as those familiar with the art areaware, high speed rotation of the turbine rotor 25 will cause a slightmolecular `movement of the lmetal in a radial direction causing a radialexpansion of the rotor. TheY radial expansion of the rotor causes asimultaneous axial contraction as a result ofthe outward displacement ofthe metal. This radial contraction will, unless compensated, cause anundesirable looseness in the drive connection.l By providing an axiallyurged key 27 which is constantly maintained against the end of the rotor25 by means of a heavy spring, no looseness whatever can be interjectedinto the coupling between the rotor and the drive shaft 16. v

The. spring force urging the key 27 in the axial direction is providedby means of the spring anges 29a on the nut 29., t As maybe se'en fromFigure 1, the flange 29a provides an overhanging lpwhich combines with ttherecess 29b`to permita deflection of the flange 29a upon theapplication of a high rotative torque to the ways, onesatisfactorycoupling is shown in the drawings.

There, the rotor 35 is splined to the drive member 43 which is in turnkeyed axially at 44 to the shaft 16. The rotor 35 ismaintained in itsaxial position relative to the shaft 16 bymeans of the spacer sleeve 45which cooperateswith a combinedV abutment and seal 46 to maintain therotor 35 a xed distance from the abutment 47 on the left hand end of theshaft 16.

-Pressure from the pump rotor outlet 37 may leak into the cavity48 andthis leakage is prevented from passing through the bore 15 by meansofthe seal plate 46 which cooperates with the Vspring biased rwipers 49and 50. While this arrangementhas proven very effective in preventingleakage of the pressurized uid medium,lit is to be understood thatotherv types of seals may be utilized if desired without departingn romthe scope of the present invention. i

As may be seen from avconsideration of Figure l, the pressurized fluidentering thecollectng ringr39Y from the pump rotor 35 may circulate pastthe radial reenforcing ribs' 51-into the portion of the collecting ring39 imme'. jdiately within the innerwall13b of the housingf13. Thus,`thecompressed uid circulates in heat transfer relationship with theincoming compressedair within the turbine inlet housing 13.V Likewise,the' iluid from the pump rotor 35 is also in heat transfer relationshipwith the bearings 17 and 18 which are tixedly mounted within the bore15. It will be apparent, therefore, that when the bearings 17 and 18develop excessive heat, heat will be dissipated to the compressed iluidin the collecting nut 29. Thus, when the nut 29 is tightened downagainst the key 27, the ange 29a is deected and a resilient set isprovided therein. When during operation the rotor 25 contracts axially,the ange 29a will move axially with the key 27 to maintain the key intight engagement with the rotor 25, and the rotor itself in tightengagement 4with the abutment plate 26 thereby providing a constant,extremely tight, connection.

. In Vthe second place, an extremely eflicient coupling is providedthrough the use of the radial key 27 since the strength of the hub ofthe rotor 25 is increased through the lelimination of axially extendingspline grooves of the conventional type. AV very small hub may beprovided in the rotor 25 when a key of the type shown at 2,7 isVutilized since the ,machiningl of a diametrical slot for the key 27does not materially affect the radial bursting strengthv of the hub.This is an improvement over the conventional type of'splne couplingwherein the splines act as` notches in the effective diameter of the huband `greatly reduce itsbursting strength.: Jlt should be remembered thatthe axially extendngsplines of a conventional connection not onlydetract from the strength of the hub through a reduction in the metal,and hence the .effec- 1 tive thickness of the hub, butalso provide anotch elect Vterial only. Q

ring 39, as well as to the' compressed gas within the causing alocalization of the stresses at the'minimum radial thicknessI of thehub. This concentration of stress causes a serious weakening of the hub,which is substantially in excess of the weakening effect of the removalof ma- The apparatus ofthe present invention includes an Vextremelysimple turbine nozzle and vane construction. Through the useof ,a smalldiameter hub, as above described, short rotor vanes 25a, which vanesextend axially relatively a great distance, may be provided. By means 'f.thi'svconstructiom la 'minimumniunber of turbine 'buckets'may be'provided thereby providing a large flow area. This permits thedevelopment of'a "considerable amount of power compared toVlargerdiameter turbines j in.which a 'greater percentage of the-airpassageway must of necessity comprise vane structure.- v Y Simplifiedmaxrufacture` of the nozzle and rotor of t the turbine is providedthrough the provision of. the exhaust housing 14 as a combined 'shroudfor the rotor and shroud forv the nozzle blades. As may be seen frontaconsideration of Figure 1, the housing 14 provides an outer peripheralconfining surface for the air throughout its llow through the nozzleopenings 3G as well as 'its diffusion in the turbine blading 25a.VThrough this arrangement, a simple, single, outer shroud element f4 ispermitted. Further, the elimination of the need of any outer shroud foreither the rotor 25 or the nozzle structure 30 permits the manufactureof both the rotor and the nozzle by means of conventional millingcutters. Thus, the blading 30a of the nozzle blade 3f) may bemanufactured by indexing the blade 30 on a conventional milling machineand moving the milling cutter in a direction of the arrow 55 shown inFigure l relative to the plate 30. Movement of the milling cutter alongthe line indicated by the arrow 55 will automatically cause a convergingnozzle passage 30h to be cut into the plate 3G.

The above method of manufacture is extremely simple and, further, may beutilized with only a slight modi-.

iication to provide a nozzle capable of supersonic operation. Thus, asmay be seen from a consideration of Figures 4 and 7, a nozzle plate 60may be provided with converging-diverging nozzle passageways 60a bysetting up the milling machine as above described and passing themilling cutter along a helical path shown by the arrow 66 in Figures 4and 7, and then tilting the nozzle plate 60 in the opposite directionabout its central axis relative to the longitudinal axis lovand passingthe milling cutter along a helical path indicated by the arrows 67 inFigures 4 and 7.

This two step milling operation provides a converging nozzle passagewayin the direction of the arrow 66 until the minimum area neck 68 isreached, at which time the passage begins to diverge. Since, as is wellknown in the art, a continuous flow passage which is to excelerate thevelocity of a gas from an initial sub-sonic value to -a supersonic valuemust comprise a convergent nozzle passage followed by a divergingsection, it will be apparent that the nozzle passageways manufactured asabove described, will operate suitably to provide supersonic flowentering the turbine wheel l5, thus providing extremely high speed, aswell as eicient, operation. Likewise, as is well known, the provision ofa continuously converging nozzle passageway as shown in Figure l willprovide an increasing velocity of the gas reaching a maximum of the'speed of sound as it leaves the nozzle passages and enters the rotorl5.

From the above discussion, it will be apparent that the nozzle platesconstructed according to the present invention may very simply bemanufactured through the use of conventional milling machines ratherthan extremely complex machinery ordinarily used for the manufacture ofnozzle passageways. This permits extremely inexpensive construction, andin many cases even more important, permits manufacture of such pump andturbine structures by manufacturing concerns not having the complexmachinery ordinarily associated with manufacture of turbine nozzle andother complex turbine blade forms. This simplified blading, when takenwith the remainder of the very compact structure provides an unusuallysimple and thermodynamically superior pump and turbine structure capableof eicient use where compactness, efficient cooling and simplicity arerequired.

It will be apparent to those skilled in the art that we have provided anovel and unusually efficient pump and turbine. It will be understoodthat various modifications may be made in the structure above set outwithout departing from the novel concepts of the present invention andwe do not, therefore, desire to be limited other than by the scope ofthe appended claims.

We claim as our invention:

l. A combined turbine and pump comprising a turbine having an annularturbine supply chamber for delivering a compressed fluid axially to aturbine rotor, means introducing Va compressediluid to saidV supplychamber, a pump having an annular collection chamber with a lateraloutlet therein for delivering a second pressurized fluid to the lateralpump outlet, sealing means preventing an intermixture of the two fluids,and a shaft rigidly connecting said turbine and said pump forsimultaneous rotation, vsaid shaft being rotatably mounted within andconcentric to said supply chamber and to said collection chamber andsaid collection chamber'beingy concentric with" and at least 'ipartially telescoped within said supply chamber and in heat transferrelation therewith.

2. A` combined turbine and pump comprising a turbine having an annularturbine supply chamber for delivering a compressed fluid axially to aturbine rotor, means intro-ducing compressed fluid to said supplychamber, a pump having an annular collection chamber with a lateraloutlet therein for delivering a second pressurized fluid to the lateraloutlet, sealing means preventing an intermixture of the two fluids, ashaft rigidly connecting at its opposite ends said turbine rotor andsaid pump for simultaneous rotation, bearing means for said shaft, saidbearing means being supported within and in heat transferring relationto said collection chamber, said shaft being rotatably mounted withinand concentric to said supply chamber and said collection chamber, saidchambers being telescoped and in heat transfer relation with each otherand said bearing means.

3. A combined turbine and pump comprising a turbine having an annularturbine supply chamber for delivering a compressed uid axially to aturbine rotor, means introducing compressed fluid to said supplychamber, a pump having an annular collection chamber with a lateraloutlet therein for delivering a second pressurized fluid to the lateraloutlet, sealing means preventing an intermixture of the vtwo fluids, ashaft rigidly connecting at its opposite ends said turbine and said pumpfor simultaneous rotation bearing means for said shaft, said shaft beingrotatably mounted within said bearing means within and concentric tosaid supply chamber and said collection chamber, said bearing meansbeing supported within and in heat transferring relation to saidcollection chamber, and said collection chamber being concentric withand at least partially telescoped within said supply chamber and in heattransfer relation therewith.

4. A combined turbine and pump comprising a turbine having an annularturbine supply chamber for delivering a compressed fluid axially to aturbine rotor, means introducing compressed fluid to -said supplychamber, a pump having an annular collection chamber with a lateraloutlet therein for delivering a second pressurized iiuid to the lateraloutlet, sealing means preventing an intermixture of the two fluids, ashaft rigidly connecting said turbine and said pump for simultaneousrotation, bearing means for said shaft, said shaft being mounted withina concentric to said supply chamber and said collection chamber, saidbearing means being supported within and in heat transferring relationto said collection chamber and said supply chamber, and said collectionchamber being concentric with and at least partially telescoped withinsaid supply chamber and in heat transfer relation therewith, saidlateral outlet being axially spaced from opposite ends of the collectionchamber.

5. A combined turbine and pump comprising a turbine having an annularturbine supply chamber for delivering a compressed fluid axially througha nozzle plate to a turbine rotor, means introducing compressed fluid tosaid supply chamber, a pump having an annular collection chamber with alateral outlet therein for delivering a second pressurized fluid to thelateral outlet, sealing means preventing an intermixture of the twofluids, and a shaft rigidly connecting said turbine and said pump forsimultaneous rotation, bearing means for said References Cited in the leof this patent UNITED STATES PATENTS Schellens Aug. 6, 1929 SchleyerJune 16, 1931 8 Bigelow Ian. 17, 1933 Buchi May 23, 1939 Browne July 11,1939 Schutte Dec. 19, 1939 Larrecq Aug. 27, 1946 Clegern Mar. 29, 1949Davis4 Dec. 18, 1951 Musikant June 10, 1952 Aue July 8, 1952 Coding Oct.14, 1952 Wheatley et a1. June 2, 1953 .nah

